EP0312151B1 - Schichtstoff aus Metallschichten und aus durchgehendem faserverstärktem synthetischem Material - Google Patents

Schichtstoff aus Metallschichten und aus durchgehendem faserverstärktem synthetischem Material Download PDF

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Publication number
EP0312151B1
EP0312151B1 EP88202179A EP88202179A EP0312151B1 EP 0312151 B1 EP0312151 B1 EP 0312151B1 EP 88202179 A EP88202179 A EP 88202179A EP 88202179 A EP88202179 A EP 88202179A EP 0312151 B1 EP0312151 B1 EP 0312151B1
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EP
European Patent Office
Prior art keywords
laminate
glass filaments
metal sheets
laminate according
glass
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EP88202179A
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English (en)
French (fr)
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EP0312151A1 (de
Inventor
Laurens Boudewijn Vogelesang
Gerardus Hubertus Joannes Joseph Roebroeks
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Akzo NV
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Akzo NV
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/18—Layered products comprising a layer of metal comprising iron or steel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
    • C03C13/00—Fibre or filament compositions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/51—Elastic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/54—Yield strength; Tensile strength
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495—Thickness [relative or absolute]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal
    • Y10T428/31681—Next to polyester, polyamide or polyimide [e.g., alkyd, glue, or nylon, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
    • Y10T442/60—Nonwoven fabric [i.e., nonwoven strand or fiber material]
    • Y10T442/654—Including a free metal or alloy constituent
    • Y10T442/656—Preformed metallic film or foil or sheet [film or foil or sheet had structural integrity prior to association with the nonwoven fabric]

Definitions

  • Laminate of metal sheets and continuous glass filaments-reinforced synthetic material Laminate of metal sheets and continuous glass filaments-reinforced synthetic material
  • the invention relates to a laminate composed of at least two metal sheets each having a thickness of less than 1.5 mm, more particularly of 0.1 to 0.8 mm, between which there is provided a synthetic layer bonded to the metal sheets, which layer contains continuous glass filaments having a modulus of elasticity greater than 50 GPa and extending parallel to each other in at least one direction, said glass filaments constituting 35-75% by volume of said synthetic material and the glass filaments combined.
  • Such a laminate is known from Dutch Patent Application Nos. 8 100 087 and 8 100 088.
  • Said E-glass as a rule substantially consists of 55% by weight of SiO2, 15% by weight of Al2O3, 19% by weight of CaO, 7% by weight of B2O3, and 3% by weight of MgO, and optionally of small amounts of other materials.
  • reinforcement filaments and fibres of E-glass have for dozens of years been applied successfully on a very wide scale for reinforcing synthetic materials.
  • reasonable results may in principle be obtained using the known laminate composed of an E-glass filaments-reinforced synthetic layer mentioned in the opening paragraph, the performance of these known laminates is not optimal when subjected to particular frequently occurring load situations.
  • the known laminate in particular is not always fully capable of meeting the high demands on the blunt notch behaviour of a construction panel in air- and spacecraft engineering.
  • the invention has for its object to provide a laminate of the type mentioned in the opening paragraph, in which the aforesaid drawbacks have been overcome.
  • the laminate according to the invention is characterized in that the glass filaments have a modulus of elasticity of the metal sheets consisting of a material having a tensile strength greater than 0.20 GPa.
  • the laminate according to the invention is with advantage characterized in that the tensile strength of the glass filaments is at least 4 GPa, more particularly 4-6 GPa, and their elongation at rupture at least 4%, more particularly 5-6%, the density of the glass filaments is 2,4-2,5 g/cm3, the diameter of each of the glass filaments 5-25 ⁇ m, more particularly 8-12 ⁇ m, the metal sheets consist of a material having a tensile strength higher than 0,35 GPa, the number of metal sheets is in the range of 2 to 20, the glass filaments are covered with a substance for bonding them to the synthetic material, and the glass filaments constitute 40-65% by volume of the total volume of synthetic material and glass filaments combined.
  • the metal sheets in the laminate may be of a metal selected from the following group of materials: steel, aluminium alloy, more particularly aluminium-copper alloys, such as those of the AA(USA) No. 2024 type or aluminium-zinc alloys, such as those of the AA(USA) No. 7075 type, titanium alloys, copper alloys and magnesium alloys.
  • a preferable embodiment of the laminate according to the invention is characterized in that the synthetic layer is composed of one or more layers of plastics-impregnated glass filaments, the filament layers being provided on either side with a synthetic boundary layer contacted by the metal sheets and bonded thereto, which boundary layers contain virtually no glass filaments and have a thickness each of 10-60 ⁇ m.
  • Favourable results have been attained using a laminate characterized according to the invention in that the synthetic layer consists of a non-thermoplastic synthetic material, such as epoxy resin, unsaturated polyester resin, vinyl esters, or phenol resins.
  • the synthetic layer should according to the invention be of a thermoplastic synthetic material.
  • a virtually amorphous thermoplastic synthetic material having a glass transition temperature Tg of at least 80°C, more particularly above 130° or 140°C, preferably above 160°C, such as polyarylate (PAR), polysulphone (PSO), polyethersulphone (PES), polyetherimide (PEI), or polyphenylene ether (PPE), more particularly poly-2,6 dimethyl phenylene ether.
  • thermoplastic synthetic material having a crystalline melting point Tm of at least 130°C, more particularly above 170°C, and preferably above 270°C, such as polyphenylene sulphide (PPS) polyamide-4,6, polyketone sulphide, polyether ketones, more particularly polyether-ether ketone (PEEK), polyether ketone (PEK), and polyether ketone-ketone (PEKK), or liquid crystal polymers, such as XYDAR® of Dartco composed of the monomers bisphenol, terephthalic acid, and hydroxybenzoic acid.
  • PPS polyphenylene sulphide
  • PEEK polyether-ether ketone
  • PEK polyether ketone
  • PEKK polyether ketone-ketone
  • liquid crystal polymers such as XYDAR® of Dartco composed of the monomers bisphenol, terephthalic acid, and hydroxybenzoic acid.
  • the blunt notch behaviour of the laminate according to the invention is more favourable than that of the aforementioned known laminate with E-glass filaments, and that the laminate according to the invention will even display a more favourable blunt notch behaviour than a solid sheet of an aluminium alloy.
  • solid sheets of aluminium alloys display a particularly favourable blunt notch behaviour.
  • blunt notch behaviour of a constructional component is meant the influence of a structural distortion in the material on the tensile strength. As distortions in the material in the form of bolt holes, passages for cables or lines will occur frequently, the favourable blunt notch behaviour of the laminate according to the invention should be considered a significant advantage in actual practice.
  • the glass filaments applied in the laminate according to the invention have a greater rigidity than the E-glass filaments used in the known laminates, as a result of which fatigue cracks in the laminate according to the invention will less readily propagate. Consequently, the laminates according to the invention display a lower crack propagation rate than the known laminates based on E-glass filaments.
  • the synthetic layer consists of a thermoplastic synthetic material
  • the several constituent layers of the laminate will have to be compressed during manufacture at a relatively high processing temperature, e.g. about 200° to 400°C, depending on the type of synthetic material used.
  • This high processing temperature will lead to the presence in the laminate of quite high residual stresses after it has been cooled to room temperature owing to the different coefficients of expansion of the metal sheets and the glass filaments.
  • such unfavourable residual stresses with tensile stresses prevailing in the metal sheets and compressive stresses in the glass filaments, may be eliminated in a simple manner by subjecting the laminate in its entirety to a pre-stressing treatment.
  • the laminate in its entirety is so elongated that the metal sheets are subject to plastic deformation without causing the glass filaments to break.
  • the laminate After the laminate has been prestressed to a sufficient degree, compressive stresses will prevail in the metal sheets of the externally entirely unloaded laminate and tensile stresses in the glass filaments.
  • the laminate may be sufficiently pre-stressed in a simple manner. Consequently, even when use is made of a synthetic layer of a thermoplastic synthetic material having a very high processing temperature of about 400°C, an optimally applicable end laminate may be obtained after said pre-stressing. It is further expected that the compressive properties of the laminate according to the invention are more favourable than those of the known laminate with reinforcement filaments of E-glass.
  • FR-A-1357393 which describes the composition of S-glass fibres per se. It is indicated (see page 1) that these glass fibres may be used as reinforcement in organic materials for use in aircraft.
  • EP-A-0 013 164 which relates to a laminate comprising a relatively thick thermoplastic layer of synthetic material covered on both sides with a thinner metal layer.
  • the layer of synthetic material may optionally contain glass fibres (see page 47, 48).
  • the fibres contained in the thermoplastic core material of this known laminate are to be in the form of randomly oriented short discontinuous fibres in order to permit the required considerable and ready deformation of the laminate, particularly when used in panels for automobile bodies (see claim 41).
  • S-glass fibres is not mentioned in this publication.
  • Fig. 1 To illustrate the advantages of the laminate according to the invention a comparison was made in Fig. 1 between the blunt notch behaviour of test specimens of the laminate according to the invention and the blunt notch behaviour of several other materials. To that end the nett tensile strength in MPa is plotted on the ordinate and the magnitude of the stress concentration factor K t on the abscissa. The curve of the blunt notch behaviour of test specimens of the laminate according to the invention is depicted by the line indicated with ALGLA-2S42. Said laminate is composed of two sheets of aluminium-copper alloy of the AA(USA) No. 2024-T3 type with a thickness each of 0,4 mm. The glass filaments were of the type marketed by Owens Corning Fiberglas under the trademark S2®-glass.
  • the modulus of elasticity of the S2®-glass filaments used was about 88,5 GPa, the tensile strength about 4,7 GPa, the elongation at rupture about 5,4%, the density 2,5 g/cm3, and the linear coefficient of expansion about 2,5.10 ⁇ 6 mm/mm/°C.
  • the S2®-glass filaments used each had a diameter of about 10 ⁇ m and were introduced into a thermosetting synthetic matrix based on epoxy resin of the AF163-2 type marketed by Minnesota Mining and Manufacturing Company.
  • the glass filaments formed 50% by volume of the total volume of synthetic material and glass filaments.
  • the prepreg formed by the glass filaments-reinforced synthetic layer had a total thickness of about 0,3 mm and during the manufacture of the laminate it was placed in between the two aluminium sheets and intimately attached to them.
  • the laminate according to the invention was not pre-stressed.
  • the curve of the blunt notch behaviour of a prior art laminate is illustrated in Fig. 1 by the dash ALGLA-2E42 line.
  • the only difference between such a laminate and the laminate according to the invention is that the reinforcement filaments are of E-glass instead of S2®-glass.
  • E-glass having a modulus of elasticity of about 74 GPa, a tensile strength of about 3,5 GPa, an elongation at rupture of about 4,8%, a density of about 2,6 g/cm3, and a linear coefficient of expansion of about 5,1 ⁇ 10 ⁇ 6 mm/mm/°C.
  • Fig. 1 the blunt notch behaviour of two solid sheets of two different aluminium alloys, viz. aluminium-zinc alloy of the AA(USA) No. 7075-T6 type and aluminium-copper alloy of the AA(USA) No. 2024-T3 type.
  • Fig. 1 the blunt notch behaviour of two solid sheets of two different aluminium alloys, viz. aluminium-zinc alloy of the AA(USA) No. 7075-T6 type and aluminium-copper alloy of the AA(USA) No. 2024-T3 type.
  • the blunt notch behaviour of the ALGLA-2S42 laminate according to the invention is considerably more favourable than that of the comparable prior art ALGLA-2E42 laminate.
  • the blunt notch behaviour of the ALGLA-2S42 laminate according to the invention also is more favourable than that of solid sheets of the 7075-T6 and 2024-T3 aluminium alloys.
  • Fig. 1 shows that for a stress concentration factor above about 2,2 the blunt notch behaviour of the prior art laminate ALGLA-2E42 is even more unfavourable than that of a simple solid sheet of 7075-T6 aluminium alloy.
  • the stress concentration factor K t is calculated in a manner conventional in the art using the formula wherein
  • ⁇ peak the peak stress in the sheet material at the end of the distortion, which may for instance be in the form of a circular hole or a slot.
  • ⁇ nominal the tensile stress at the distortion calculated from the tensile strength divided by the remaining (nominal) surface area of the cross-section of the test bar at the distortion.
  • Fig. 2 gives test results showing the influence on the tensile strength of a (sharp) saw-cut crack in the sheet material.
  • the nett tensile strength in MPa is plotted on the ordinate and the length of the previously made crack or saw-cut transverse to the direction of drawing is plotted on the abscissa.
  • the shape of the test specimens of sheet material used is also drawn in Fig. 2.
  • the variation in the residual tensile strength or residual strength for test specimens of the laminate according to the invention is illustrated by the line indicated with ALGLA-2S32. The only difference between this laminate and the ALGLA-2S42 laminate described with reference to Fig.
  • FIG. 1 consists in that the aluminium sheets in the ALGLA-2S32 laminate each have a thickness of 0,3 mm.
  • the ALGLA-2S32 curve was plotted by constantly repeated tests on the drawn test specimens in which (sharp) saw-cut cracks of a total length 2a of 10 mm, 30 mm, or 60 mm had been made.
  • the curve of the residual strength for test specimens of the prior art laminate is given by the dash line indicated with ALGLA-2E32.
  • the only difference between said laminate and the ALGLA-2E42 laminate described with reference to Fig. 1 consists in that the aluminium sheets in the ALGLA-2E32 laminate each have a thickness of 0,3 mm.
  • FIG. 2 shows the curve of the residual strength for test specimens of solid sheet material indicated with the line 2024-T3 for the aluminium-copper alloy of the same designation.
  • the ALGLA-2S32 laminate according to the invention displays a more favourable residual strength behaviour in the case of relatively sharp cracks than does the comparable prior art ALGLA-2E32 laminate.
  • Fig. 2 also demonstrates that said residual strength behaviour of the laminate according to the invention is more favourable than that of solid sheet material of copper-aluminium alloy of the AA(USA) 2024-T3 type.
  • Fig. 3 the fatigue performance of test specimens of the laminate according to the invention of the ALGLA-2S32 type described earlier is depicted in comparison with that of the earlier described prior art ALGLA-2E32 laminate.
  • the fatigue performance of test specimens of solid sheet material of 2024-T3 aluminium-copper alloy is also given in Fig. 3.
  • the half lengths of the crack are plotted on the ordinate.
  • On the abscissa is plotted the total number of cycles of the used sinusoidally varying tensile fatigue load at constant amplitude.
  • the frequency of the varying load was 10 Hertz.
  • the ALGLA-2S32 laminate according to the invention displays a lower crack propagation rate under the influence of said varying load than does the ALGLA-2E32 prior art laminate. It may therefore be concluded that the fatigue performance of the laminate according to the invention is more favourable than that of the prior art laminate. Both laminates display a far more favourable fatigue performance than does the laminate of solid sheet material of aluminium-copper alloy of the 2024-T3 type.
  • Figure 4 illustrates the fatigue performance of test specimens of the laminate according to the invention of the earlier-described ALGLA-2S32 type in comparison with the earlier described ALGLA-2E32 prior art laminate, use being made, however, of a somewhat different type of load.
  • Fig. 4 again the half crack lengths are plotted on the ordinate.
  • abscissa is plotted again the total number of cycles of the used varying tensile fatigue load at constant amplitude.
  • the variation in load is not sinusoidal but more or less block shaped, as is shown schematically in Fig. 4.
  • the frequency of this varying load is only 0,02 Hertz.
  • the fatigue load used is therefore also of the type.
  • the ALGLA-2S32 laminate according to the invention displays less crack propagation under the influence of this type of varying load than does the ALGLA-2E32 prior art laminate. Consequently, the fatigue performance of the laminate according to the invention for this type of load is more favourable than that of the prior art laminate.
  • Fig. 5 is a schematic drawing in perspective of an embodiment of the laminate according to the invention generally referred to by the numeral 1.
  • the laminate 1 consists of two metal sheets 2 with in between them a prepreg 3 composed of a synthetic layer reinforced with a very large number of parallel or unidirectional threads or filaments 4 of glass.
  • the synthetic layer 3 may be made up of a core layer of plastics-impregnated filaments 5 and on either side of it a boundary layer 6 intimately attached to the metal sheets 2, the boundary layers containing virtually no filaments.
  • Fig. 6 is a cross-sectional view of a laminate 1 according to the invention, which differs from the laminate according to Fig. 5 only in that it is composed of three metal sheets 2 with in between them two synthetic layers 3 reinforced with parallel glass filaments 4.
  • the manufacture of the laminate according to the invention shown in Fig. 5 first of all comprised the superimposition, on a movable support, of two identical metal sheets of an appropriate aluminium alloy with interposition of said prepreg, which may for instance be composed of a large number of parallel (unidirectional) continuous glass filaments impregnated with a thermosetting synthetic material based on epoxy resin. While on the support, the resulting laminate of loose parallel parts, viz. two metal sheets with in between them the prepreg, was covered with a film. Next, the laminate wrapped in film and still consisting of loose parts was compressed externally by creating a vacuum inside the wrapping of the laminate. The wrapped laminate along with its moveable support was then placed in an autoclave.
  • the laminate in it was subjected to an air pressure of 4 bar and the temperature was increased to 120°C. After a 66 minutes stay in the autoclave the laminate was finished and it was removed from the autoclave.
  • the cooled laminate may also be pre-stressed in the manner described earlier, such that in the metal sheets of the laminate in its externally entirely unloaded state there prevails a compressive stress and in the filaments a tensile stress.
  • the metal sheets Before being attached to the prepreg, the metal sheets should of course be subjected to various appropriate pre-treatments, such as alkaline degreasing, etching in a chromic-sulphuric acid bath, anodizing in chromic acid or phosphoric acid, application of a primer appropriate to the type of synthetic material used, e.g. on a basis of epoxy phenol and having corrosion inhibiting properties, or the like.
  • pre-treatments such as alkaline degreasing, etching in a chromic-sulphuric acid bath, anodizing in chromic acid or phosphoric acid, application of a primer appropriate to the type of synthetic material used, e.g. on a basis of epoxy phenol and having corrosion inhibiting properties, or the like.
  • tensile strength of the glass filaments used in the description invariably refers to the virgin tenacity at tensile load in the longitudinal direction of the filament and measured on a single filament containing no adhesives, i.e. a virgin filament, the measurements being carried out in accordance with ASTM NO. D3379-75.
  • the modulus of elasticity also has to be determined in accordance with ASTM No. D3379-75.
  • T g of said substantially amorphous thermoplastic synthetic materials should be determined employing a dynamic mechanical measuring device of the RDA-700 type of the make Rheometrics, using a frequency of 1 Hertz and a heating rate of 2°C/min. at most.
  • T g is the temperature at which there is a maximum damping modulus G ⁇ .
  • T m of the semi-crystalline thermoplastic synthetic materials is determined by Differential Scanning Calorimetry (DSC). This determination is carried out with the DSC-7 type measuring apparatus of Perkin Elmer at a heating rate of 20°C/min. T m is defined here as the peak maximum of the endo-thermical peak in the DSC curve.
  • the laminates according to the invention it is preferred that use be made of metal sheets having the same thickness, it is in principle also possible for one and the same laminate to contain metal sheets which have two or more thicknesses and are arranged symmetrical or not. As a rule, the thickness of the synthetic layer between two successive metal sheets will be of approximately the same order of magnitude as that of each of the metal sheets.
  • the synthetic layer may contain some conventional additions such as fillers.
  • the continuous reinforcing threads or filaments in the synthetic layers may extend parallel to each other in one direction, i.e., they may be arranged unidirectional.
  • Such an arrangement may for instance be realized by providing the filaments of the two groups in the form of a fabric.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Geochemistry & Mineralogy (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)

Claims (9)

1. Laminat aus mindestens zwei Metallblechen, von denen jedes eine Dicke von weniger als 1,5 mm, insbesondere von 0,1 bis 0,8 mm besitzt, wobei zwischen den Blechen eine Kunststoffschicht angeordnet ist, welche mit den Metallblechen verklebt ist, welche Schicht Glasfilamente mit einem Elastizitätsmodul von über 50 GPa enthält, die mindestens in einer Richtung parallel zueinander liegen, wobei die Glasfilamente 35-75% des Volumens des Kunststoffes und der Glasfilamente zusammen bilden, dadurch gekennzeichnet, dass
A. die Glasfilamente einen Elastizitätsmodul von 80-100 GPa haben;
B. die Glasfilamente 58-69 GEw.%, vorzugsweise 60-65 Gew.% SiO₂ enthalten;
C. die Glasfilamente 18-29 Gew.%, vorzugsweise 20-25 Gew.% Al₂O₃ enthalten;
D. die Glasfilamente 7-19 Gew.%, vorzugsweise 9-15 Gew.% MgO enthalten;
E. die Metallbleche aus einem Material mit einer Zugfestigkeit von über 0,20 GPa bestehen.
2. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Zugfestigkeit der Glasfilamente 4-6 GPa beträgt.
3. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Bruchdehnung der Glasfilamente 4-6% beträgt.
4. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Zahl der Metallbleche im Bereich von 2 bis 20 liegt.
5. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Dicke der Kunststoffschicht zwischen zwei aufeinanderfolgenden Blechen kleiner ist, als die jedes der Bleche.
6. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Kunststoff und Glasfilamente enthaltende Schicht ein duroplastisches Material enthält.
7. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Kunststoff und Glasfilamente enthaltende Schicht einen thermoplastischen Kunststoff enthält.
8. Laminat nach Anspruch 1, dadurch gekennzeichnet, dass die Metallbleche aus einem Metall aus folgender Werkstoffgruppe bestehen: Aluminiumlegierungen, insbesondere Aluminium-Kupfer-Legierungen, wie solche vom Typ AA(USA) No. 2024, oder Aluminium-Zink-Legierungen, wie solche vom Typ AA(USA) No. 7075, Stahl, Titaniumlegierungen, Kupfer, Kupferlegierungen und Magnesiumlegierungen.
9. Flugzeugrumpf, dadurch gekennzeichnet, dass das Oberschalenblech aus einem Laminat nach Anspruch 1 besteht.
EP88202179A 1987-10-14 1988-10-03 Schichtstoff aus Metallschichten und aus durchgehendem faserverstärktem synthetischem Material Expired - Lifetime EP0312151B1 (de)

Priority Applications (1)

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AT88202179T ATE61970T1 (de) 1987-10-14 1988-10-03 Schichtstoff aus metallschichten und aus durchgehendem faserverstaerktem synthetischem material.

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NL8702453 1987-10-14
NL8702453 1987-10-14

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EP0312151A1 EP0312151A1 (de) 1989-04-19
EP0312151B1 true EP0312151B1 (de) 1991-03-27

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US (1) US5039571A (de)
EP (1) EP0312151B1 (de)
JP (1) JP2660563B2 (de)
AT (1) ATE61970T1 (de)
CA (1) CA1306936C (de)
DE (1) DE3862185D1 (de)
ES (1) ES2022602B3 (de)
GR (1) GR3002178T3 (de)

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Also Published As

Publication number Publication date
US5039571A (en) 1991-08-13
JPH01136736A (ja) 1989-05-30
JP2660563B2 (ja) 1997-10-08
DE3862185D1 (de) 1991-05-02
GR3002178T3 (en) 1992-12-30
ES2022602B3 (es) 1991-12-01
CA1306936C (en) 1992-09-01
EP0312151A1 (de) 1989-04-19
ATE61970T1 (de) 1991-04-15

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